Steven Lyle Weiner

US Patent:

D524229, Jul 4, 2006

Filed:

May 30, 2005

Appl. No.:

29/231088

Inventors:

Brandon Stille - Cheshire CT, US
Steven D. Weiner - Orange CT, US
Leslie Schweizer - Cayuta NY, US
Michael P. Strauss - New Haven CT, US
Matthew J. Tarascio - Milford CT, US
Mark W. Scott - Bethany CT, US

Assignee:

Sirorsky Aircraft Corporation - Stratford CT

International Classification:

1207

US Classification:

D12327

US Patent:

D524230, Jul 4, 2006

Filed:

May 31, 2005

Appl. No.:

29/231089

Inventors:

Brandon Stille - Cheshire CT, US
Steven D. Weiner - Orange CT, US
Michael P. Strauss - New Haven CT, US
Matthew J. Tarascio - Milford CT, US

Assignee:

Sikorsky Aircraft Corporation - Stratford CT

International Classification:

1207

US Classification:

D12327

US Patent:

7954766, Jun 7, 2011

Filed:

Jun 19, 2006

Appl. No.:

11/455482

Inventors:

Steven J. Brainard - Cheshire CT, US
David R. Houy - Shelton CT, US
Anthony Z. Stobiecki - Huntington CT, US
Mark W. Scott - Bethany CT, US
Steven D. Weiner - Orange CT, US

Assignee:

Sikorsky Aircraft Corporation - Stratford CT

International Classification:

B64D 47/00

US Classification:

244194, 701124, 73 6505

Abstract:

An interactive aircraft load management system automates calculation and provides simulation capability to changes in an aircraft C. G. limit for display on a three-dimensional aircraft symbology. The aircraft load management system also communicates with a fly by wire (FBW) flight control system wherein the aircraft's control system is programmed to automatically compensate for C. G. excursions and to alter control laws. The aircraft load management system also selectively reels-in and reels out sling lines as the aircraft pitches and rolls to maintain a load vector from a slung load along the aircraft centerline. Load vector travel is accomplished by coupling a winch control system into the flight control system.

US Patent:

8636248, Jan 28, 2014

Filed:

Mar 2, 2012

Appl. No.:

13/410749

Inventors:

Brandon L. Stille - Cheshire CT, US
Steven D. Weiner - Orange CT, US

Assignee:

Sikorsky Aircraft Corporation - Stratford CT

International Classification:

B64C 25/00

US Classification:

244109

Abstract:

A tailwheel assembly for an aircraft includes a ventral fin including a fixed airframe portion of the ventral fin and a moveable tailwheel portion of the ventral fin. A tailwheel strut extends through the ventral fin and includes a fixed first strut portion and an extendable second strut portion having the moveable tailwheel portion of the ventral fin secured thereto. A tailwheel is secured to the extendable second strut portion. A method of operating a tailwheel assembly for an aircraft includes extending an extendable portion of a tailwheel strut from an airframe of the aircraft. The tailwheel strut has a tailwheel secured thereto and is located at least partially in a ventral fin of the aircraft. A tailwheel portion of the ventral fin is moved away from a fixed airframe portion of the ventral fin via extension of the extendable portion of the tailwheel strut.

US Patent:

20020040355, Apr 4, 2002

Filed:

Jul 26, 2001

Appl. No.:

09/915737

Inventors:

Steven Weiner - Merrick NY, US

International Classification:

G06F017/00

US Classification:

705/412000

Abstract:

A system for remote payment of utility usage including a customer terminal and a utility provider server wherein the customer terminal includes a utility meter for collecting utility usage data and an input device configured to receive customer account information. At any time during a billing cycle, a customer may prompt the customer terminal to make payment by inserting account information into the customer terminal. The utility provider server may communicate with the customer terminal to transmit and receive customer account information, payment information, usage data, rate data, and other information.

US Patent:

51316048, Jul 21, 1992

Filed:

Apr 11, 1991

Appl. No.:

7/683904

Inventors:

Charles A. Yoerkie - Newington CT
Philip H. LeMasurier - New Fairfield CT
Steven D. Weiner - Orange CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

B64C 2782

US Classification:

244 1719

Abstract:

A ducted fan antitorque device for a helicopter having an empennage structure including a shroud configured for internal mounting of the ducted fan antitorque device. The ducted fan antitorque device has a configuration optimized to provide the antitorque thrust required for helicopter yaw stability and maneuverability and to minimize the operating noise levels of the ducted fan antitorque device. The ducted fan antitorque device includes an airflow duct and a fan assembly coaxially mounted within the airflow duct. The airflow duct includes an inlet having a curved lip configuration of constant radius, a divergent duct portion downstream of and contiguous with the inlet having a predetermined divergence angle, and an outlet terminating the divergent duct portion having a curved lip configuration of variable radius. The fan assembly includes a central hub structure, a plurality of support struts for coaxially mounting the hub structure in the airflow duct, and a tail rotor subsystem rotatably mounted on the hub structure. The support struts have an elliptical configuration to enhance the aerodynamic performance and reduce the noise generated by the ducted fan antitorque device.

US Patent:

51020670, Apr 7, 1992

Filed:

Apr 11, 1991

Appl. No.:

7/683903

Inventors:

Steven D. Weiner - Orange CT
Thomas J. Toner - Milford CT
John J. Occhiato - Derby CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

B64C 2782

US Classification:

244 1719

Abstract:

An integrated empennage structure is provided for a helicopter embodying a ducted fan antitorque device. The integrated empennage structure includes a shroud that houses the ducted fan antitorque device, a vertical stabilizer, and a horizontal stabilizer. The aerodynamic configurations and/or orientations and the spatial orientations of the shroud, vertical stabilizer, and the horizontal stabilizer are interactively related and optimized to provide yaw stability and directional control and pitch stability and maneuverability required for helicopter flight operations. The shroud is spatially orientated at a first predetermined cant angle with respect to the vertical plane of symmetry of the helicopter fuselage such that the ducted fan antitorque device provides lateral antitorque thrust to counteract main rotor assembly induced torque and a positive vertical force component to enhance the overall lift capability of the helicopter. The vertical stabilizer is spatially orientated at a second predetermined cant angle with respect to the vertical plane and aerodynamically configured with a predetermined camber and/or aerodynamically orientated with a predetermined angle if incidence to provide an antitorque force during forward flight regimes that allows the ducted fan antitorque device to be effectively off-loaded and a negative vertical force component that complements the negative vertical force provided by the horizontal stabilizer. The aerodynamic functioning of the vertical stabilizer allows aerodynamic configuration and/or the aerodynamic orientation of the horizontal stabilizer to be reduced and facilitates the attachment of the horizontal stabilizer in substantially symmetrical relation to the vertical stabilizer.

US Patent:

51080443, Apr 28, 1992

Filed:

Apr 11, 1991

Appl. No.:

7/683642

Inventors:

Steven D. Weiner - Orange CT
Robert C. Moffitt - Seymour CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

B64C 2782

US Classification:

244 17190

Abstract:

A shroud-fin integration shelf for a helicopter empennage structure that includes a shroud embodying a ducted fan antitorque device, a vertical stabilizer contiguous with the shroud, and a horizontal stabilizer intersecting the vertical stabilizer. The shroud-fin integration shelf is structurally configured and dimensioned to eliminate adverse aerodynamic effects experienced by the vertical stabilizer in reverse thrust operating conditions wherein mass airflow exiting the ducted fan antitorque device may flow along the shroud and interfere with longitudinal mass airflow over the suction surface of the vertical stabilizer. The integration shelf, which provides an acute transition between the shroud and the vertical stabilizer, has an overall predetermined width that includes a first shelf width on the ducted fan antitorque device inlet side of the empennage structure and a second shelf width on the opposite side of the empennage structure. The first shelf width is greater than the second shelf width to ensure attached mass airflow over the shroud is sharply separated at the shroud - shroud-fin integration shelf. The first and second shelf widths have dimensional magnitudes in the range of about four percent to about sixteen percent of the diameter of the fan assembly of the ducted fan antitorque device.